CN104787301A - Sectional ultralight aircraft skin fast connection structure and making method thereof - Google Patents
Sectional ultralight aircraft skin fast connection structure and making method thereof Download PDFInfo
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- CN104787301A CN104787301A CN201510053727.0A CN201510053727A CN104787301A CN 104787301 A CN104787301 A CN 104787301A CN 201510053727 A CN201510053727 A CN 201510053727A CN 104787301 A CN104787301 A CN 104787301A
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Abstract
The invention discloses a sectional aircraft skin fast connection structure and a making method thereof, skin comprises left and right sections which are adjacently arranged, the left and right sections of the skin are both laid on the support surface of a truss, a connecting piece is a mushroom head type industrial fastening belt, the length of the mushroom head type industrial fastening belt is equal to the length of the skin, and the width of the mushroom head type industrial fastening belt is equal to half of the width of the support surface. The method is as follows: reasonable skin segmentation form is selected, the mushroom head type industrial fastening belt with a suitable bearing range is selected, laying and pasting of the mushroom head type industrial fastening belt on the skin are completed, mushroom type fastening pieces at the two sides of the fastening belt are pressed, and fixing of an aluminum alloy pressing plate is completed. By the way, the sectional aircraft skin fast connection structure can realize repeated disassembly and assembly, facilitates the body's maintenance and maintenance, significantly improves the usage rate of the skin, prolongs the service life of the skin, simplifies the process, reduces the weight, and reduces the cost.
Description
Technical field
The present invention relates to aircraft skin interconnection technique field, particularly relate to the ultralight aircraft skin fast joint structure of a kind of sectional type and method for making.
Background technology
Along with aircraft is to the development in lightweight direction, composite material application aboard progressively improves, become the index that of weighing aircaft configuration advance is important, simultaneously compared with metallic material, composite material is little with its thermal expansion coefficient, antifatigue and the advantage such as vibration resistance is strong, anticorrosive, can significantly reduce part, fastener quantity improves integrally-built Combination property, become one of large main material of aircraft body structure four of new generation.But compared with metal construction, the weakness such as composite material interlayer intensity is low, impact resistance is poor, the assembly connection difficulty determining its structure is large, technical requirements is high.
The connection of aircraft skin and skeleton, is usually confined to the conventional mechanical fixed form such as welding, staking and the adhesive technology of complexity.Because composite airplane skin thickness is generally 0.5mm ~ 2.5mm, this thin-wall part easily forms single point pressure when welding or staking fixes, the internal stress caused often is difficult to eliminate, for the thin-walled skin be made up of composite material, have a strong impact on intensity and the life-span of material, and the planeness of covering itself is also subject to the impact of skeleton structure, appearance is unsatisfactory.In addition, if adopt adhesive technology, different glue kinds is different with clean, bondline thickness, cure time, even work-yard ambient temperature etc. the requirements of covering adhesive surface to truss, and this adds the difficulty of assembling undoubtedly, reduces work efficiency.
Summary of the invention
The technical matters that the present invention mainly solves is to provide one can solve single-point unbalance stress and assembly difficulty is large, the not easily problem of repeated disassembled and assembled, realizes the quick position of technique for aircraft composite covering and the ultralight aircraft skin fast joint structure of sectional type of efficient assembling and method for making.
For solving the problems of the technologies described above, the technical scheme that the present invention adopts is: provide a kind of sectional type aircraft skin fast joint structure, comprise: covering, truss and the attaching parts being connected covering and truss, covering comprises left section and right section being disposed adjacent, left section of described covering and right section is all layed on the bearing surface of truss, described attaching parts is mushroom-head industry sticking belt, comprise the first mushroom fastener and the second mushroom fastener of relative snapping, the back side of described first mushroom fastener is adhered to the lower surface of left section and right section, the back side of described second mushroom fastener is adhered to the upper surface of bearing surface, the length of described mushroom-head industry sticking belt equals the length of covering, width equals the half of bearing surface width.
In a preferred embodiment of the present invention, described left section is provided with aluminum alloy pressing plate with the upper surface of right section of adjacent part, and described aluminum alloy pressing plate is fixed on bearing surface.
In a preferred embodiment of the present invention, the length and width of described left section or right section are 5000mm × 1000mm, and thickness is 0.5mm ~ 2.5mm.
In a preferred embodiment of the present invention, the peel strength of mushroom-head industry sticking belt is less than or equal to 6.66N/cm
-1, and the mushroom head diameter in the first mushroom fastener and the second mushroom fastener is more than or equal to for 0.26mm.
For solving the problems of the technologies described above, another technical solution used in the present invention is: the method for making providing a kind of sectional type aircraft skin fast joint structure, comprises the following steps:
(1) according to version and the processing technology of aircraft, rational covering segmented version is selected;
(2) the mushroom-head industry sticking belt of suitable carrying scope is selected; According to the segmented version determination sticking belt size of aircraft skin, sticking belt length equals covering length, and width equals the bearing surface width half of truss;
(3) parts that step (1) is determined are processed, comprise the cleaning of the bearing surface of covering burr and aircraft truss, the bearing surface of covering burr and aircraft truss should keep cleaning, dry;
(4) laying of mushroom head industry sticking belt on covering, stickup is completed;
First the first mushroom fastener is pasted respectively the lower surface of adjacent left section and right section by the mode of heating, then the second mushroom fastener is pasted on the upper surface of the bearing surface of truss by the mode heated;
(5) the mushroom-shaped fastener in compacting sticking belt both sides; The second mushroom fastener that adjacent left section bonds with the first mushroom fastener and the bearing surface upper surface of right section of covering lower surface is withheld;
(6) the fixing of aluminum alloy pressing plate is completed; The aluminum alloy pressing plate being used for compressing covering is fitted in the upper surface place of left and right section of adjacent part, and aluminum alloy pressing plate is fixed on the bearing surface of truss;
(7), after said structure installation, the structural adjustment of integrated airplane covering is carried out.
In a preferred embodiment of the present invention, in step (4), type of heating adopts heating rod heating, and heating-up temperature is less than or equal to 55 DEG C.
In a preferred embodiment of the present invention, described bearing surface and aluminum alloy pressing plate are all provided with at least two knock holees, the hole on aluminum alloy pressing plate and the hole coaxial positioning on bearing surface, then with flathead screw, aluminum alloy pressing plate are fixed on truss on bearing surface.
In a preferred embodiment of the present invention, in step (5), be by the roller of 10kg by fastening part when not by roll extrusion when additional force effect 5 times, finally realize first, second mushroom fastener compacting.
The beneficial effect of the ultralight aircraft skin fast joint structure of sectional type of the present invention and method for making is:
1, industrial sticking belt is applied to aircraft skin to connect, existing mechanical connection is replaced to be connected with glue, the Fast Installation of sectional type covering and efficient assembling can be realized, work efficiency improves 4 ~ 10 times, simultaneously because sticking belt can repeatedly use, maximumly can realize 100 times and repeat to close, so can also repeated disassembled and assembled be realized, be convenient to the care and maintenance of body.
2, industrial sticking belt is applied on the ultralight thin-walled aircraft skin of composite material, due to the homogeneity of glue in stress distribution, avoid single point pressure that mechanical fixed form formed and the problem of unbalance stress that glue bond technique rubber thickness asymmetry causes, simultaneously because mushroom-shaped industrial sticking belt hardness Ageing is higher than general hair side+hooks face sticking belt more than 5 times, thus the Occupation coefficient significantly improving covering with extend covering service life.
3, by industrial sticking belt and the ultralight thin-walled aircraft skin of composite material, because sticking belt can bear ground and aerial instantaneous temperature difference 65 DEG C ~-40 DEG C, ensure that stressed ageing of aircraft skin, thus avoid the situation of the intensity temperature influence of the mechanical connections such as solder joint.
4, sticking belt is hidden in below aircraft skin, the clean and smooth of aircraft skin surface can be kept, thus ensure that the good aerodynamic configuration of aircraft.
5, can be directly fixed on aircraft skin with industrial sticking belt, without the need to making installation bracing frame again in stabilator inside, thus simplify technique, alleviating weight, reducing cost.
Accompanying drawing explanation
In order to be illustrated more clearly in the technical scheme in the embodiment of the present invention, below the accompanying drawing used required in describing embodiment is briefly described, apparently, accompanying drawing in the following describes is only some embodiments of the present invention, for those of ordinary skill in the art, under the prerequisite not paying creative work, other accompanying drawing can also be obtained according to these accompanying drawings, wherein:
Fig. 1 is the structural representation of sectional type aircraft skin fast joint structure one of the present invention preferred embodiment;
Fig. 2 is the structural representation of the middle truss of the aircraft skin of sectional type shown in Fig. 1 fast joint structure;
Fig. 3 is the local structure schematic diagram at A place in truss shown in Fig. 2;
Fig. 4 is the structural representation of the middle bearing surface of the aircraft skin of sectional type shown in Fig. 1 fast joint structure;
Fig. 5 is the structural representation of the middle aluminum alloy pressing plate of the aircraft skin of sectional type shown in Fig. 1 fast joint structure;
Fig. 6 is the covering segmental structure of a preferred embodiment in sectional type aircraft skin fast joint structure of the present invention;
In accompanying drawing, the mark of each parts is as follows: 1, covering, and 2, left section, 3, right section, 4, truss, 5, bearing surface, the 6, first mushroom fastener, the 7, second mushroom fastener, 8, aluminum alloy pressing plate.
Detailed description of the invention
Be clearly and completely described to the technical scheme in the embodiment of the present invention below, obviously, described embodiment is only a part of embodiment of the present invention, instead of whole embodiments.Based on the embodiment in the present invention, those of ordinary skill in the art, not making other embodiments all obtained under creative work prerequisite, belong to the scope of protection of the invention.
The embodiment of the present invention comprises:
A kind of sectional type aircraft skin fast joint structure, comprising: covering 1, truss 4 and the attaching parts being connected covering 1 and truss 4.
As shown in Figure 1, covering 1 comprises left section 2 and right section 3 being disposed adjacent, and left section 2 of described covering 1 and right section 3 is all layed on the bearing surface 5 of truss 4.
Covering 1 mainly adopts high-performance composite materials laying plate composition, and ply stacking-sequence is: (0,90)/(± 45)/(0,90)/(± 45)/(0,90), covering 1 adopts cure process in advance.The length and width of described left section 2 or right section 3 are 5000mm × 1000mm, and thickness is 0.5mm ~ 2.5mm.
Described attaching parts is mushroom-head industry sticking belt, and its hardness Ageing higher than general hair side+hook face sticking belt more than 5 times, and has superpower anti-shear ability.As shown in Figure 3, mushroom-head industry sticking belt comprises the first mushroom fastener 6 and the second mushroom fastener 7 of relative snapping, the back side of described first mushroom fastener 6 is adhered to the lower surface of left section 2 and right section 3, the back side of described second mushroom fastener 7 is adhered to the upper surface of bearing surface 5, the length of described mushroom-head industry sticking belt equals the length of covering 1, and width equals the half of bearing surface 5 width.
The peel strength of mushroom-head industry sticking belt is less than or equal to 6.66N/cm
-1, and the mushroom head diameter in the first mushroom fastener 6 and the second mushroom fastener 7 is more than or equal to for 0.26mm.
As shown in Figure 4, the bearing surface 5 of truss 4 is also adopt high-performance composite materials laying plate composition, and main rising supports aerodynamic configuration, connects aircraft skin and wing beam action.In addition, the bearing surface 5 of truss 4, by two knock holees, plays location with fastening.
As shown in Figure 5, the upper surface of described left section 2 and right section 3 adjacent parts is provided with aluminum alloy pressing plate 8, and described aluminum alloy pressing plate 8 is fixed on bearing surface 5.The shape of aluminum alloy pressing plate 8 obtains according to skin shape, and adopt aluminum alloy material, modulus of elasticity is 70GPa, and Poisson's ratio is 0.3, plays location and compacting diaphragms effect.
The invention still further relates to a kind of method for making of sectional type aircraft skin fast joint structure, comprise the following steps:
(1) according to version and the processing technology of aircraft, select rational covering segmented version, covering 1 left section 2 or right section 3 segmentation length and width are 5000mm × 1000mm.
(2) the mushroom-head industry sticking belt of suitable carrying scope is selected; According to the segmented version determination sticking belt size of aircraft skin 1, sticking belt length equals covering 1 length, and width equals the bearing surface 5 width half of truss 4; Peel strength when maximum load determination sticking belt is stripped suffered by covering 1, sticking belt maximum peeling strength is 6.66N/cm
-1, mushroom head diameter is at least 0.26mm.
(3) parts that step (1) is determined are processed, comprise the cleaning of the bearing surface 5 of covering burr and aircraft truss 4, the bearing surface 5 of covering burr and aircraft truss 4 should keep cleaning, dry.
(4) laying of mushroom head industry sticking belt on covering 1, stickup is completed; First the first mushroom fastener 6 is pasted respectively the lower surface of adjacent left section 2 and right section 3 by the mode of heating, then the second mushroom fastener 7 is pasted on the upper surface of the bearing surface 5 of truss 4 by the mode heated; Heating rod heats, and heating-up temperature can not higher than 55 DEG C, and hand can not touch glue-line, in order to avoid grease affects the viscosity of glue on hand.
(5) the mushroom-shaped fastener in compacting sticking belt both sides; First mushroom fastener 6 of adjacent left section 2 and right section 3 covering lower surfaces is withheld with the second mushroom fastener 7 that bearing surface 5 upper surface bonds; By the roller of 10kg by fastening part when not by roll extrusion when additional force effect 5 times, finally realize first, second mushroom fastener 7 compacting.
(6) the fixing of aluminum alloy pressing plate 8 is completed; The aluminum alloy pressing plate 8 being used for compressing covering is fitted in the upper surface place of left and right section of 3 adjacent parts, the hole coaxial positioning on the hole on aluminum alloy pressing plate 8 and bearing surface 5, then with flathead screw, aluminum alloy pressing plate 8 is fixed on the bearing surface 5 of truss 4.
(7), after said structure installation, the structural adjustment of integrated airplane covering is carried out.After all structure installment complete, carry out the structural adjustment of integrated airplane covering, observe the laminating degree of covering, if any warped portion, after dismounting, readjust installation.
In one embodiment of the present invention:
The ultralight aircraft skin quick connecting method of a kind of sectional type, certain aerodone wing uses.The long 14m of the span, chord length 5m, skin thickness 0.5mm, split into shown in Fig. 6, every section of width 1000mm, as shown in Figure 1.This method of attachment is utilized to be connected by mushroom-shaped industrial sticking belt with the bearing surface 5 of truss by aerodone covering, and by aluminum alloy pressing plate 8 compacting, as shown in Figure 2.This method of attachment realizes the Fast Installation of sectional type covering and efficient assembling, work efficiency improves 8 times, simultaneously due to the homogeneity of the power transmission of sticking belt, the load with the bearing surface 5 of truss can be passed to the utmost by covering, the Occupation coefficient of covering improves greatly, and obtain good aerodynamic configuration, extend covering service life.
A kind of sectional type ultralight aircraft skin fast joint structure of the present invention and method for making are applicable to the aircraft wing of the Special Areas flights such as the more stable environment of the lower aerodone of flying speed, solar powered aircraft wing and other wind speed and advection layer.
Advantage is:
1, industrial sticking belt is applied to aircraft skin to connect, existing mechanical connection is replaced to be connected with glue, the Fast Installation of sectional type covering and efficient assembling can be realized, work efficiency improves 4 ~ 10 times, simultaneously because sticking belt can repeatedly use, maximumly can realize 100 times and repeat to close, so can also repeated disassembled and assembled be realized, be convenient to the care and maintenance of body.
2, industrial sticking belt is applied on the ultralight thin-walled aircraft skin of composite material, due to the homogeneity of glue in stress distribution, avoid single point pressure that mechanical fixed form formed and the problem of unbalance stress that glue bond technique rubber thickness asymmetry causes, simultaneously because mushroom-shaped industrial sticking belt hardness Ageing is higher than general hair side+hooks face sticking belt more than 5 times, thus the Occupation coefficient significantly improving covering with extend covering service life.
3, by industrial sticking belt and the ultralight thin-walled aircraft skin of composite material, because sticking belt can bear ground and aerial instantaneous temperature difference 65 DEG C ~-40 DEG C, ensure that stressed ageing of aircraft skin, thus avoid the situation of the intensity temperature influence of the mechanical connections such as solder joint.
4, sticking belt is hidden in below aircraft skin, the clean and smooth of aircraft skin surface can be kept, thus ensure that the good aerodynamic configuration of aircraft.
5, can be directly fixed on aircraft skin with industrial sticking belt, without the need to making installation bracing frame again in stabilator inside, thus simplify technique, alleviating weight, reducing cost.
The foregoing is only embodiments of the invention; not thereby the scope of the claims of the present invention is limited; every utilize description of the present invention to do equivalent structure or equivalent flow process conversion; or be directly or indirectly used in other relevant technical field, be all in like manner included in scope of patent protection of the present invention.
Claims (8)
1. a sectional type aircraft skin fast joint structure, comprise: covering, truss and the attaching parts being connected covering and truss, it is characterized in that, covering comprises left section and right section being disposed adjacent, left section of described covering and right section is all layed on the bearing surface of truss, described attaching parts is mushroom-head industry sticking belt, comprise the first mushroom fastener and the second mushroom fastener of relative snapping, the back side of described first mushroom fastener is adhered to the lower surface of left section and right section, the back side of described second mushroom fastener is adhered to the upper surface of bearing surface, the length of described mushroom-head industry sticking belt equals the length of covering, width equals the half of bearing surface width.
2. according to claim a kind of sectional type aircraft skin fast joint structure, is characterized in that, described left section is provided with aluminum alloy pressing plate with the upper surface of right section of adjacent part, and described aluminum alloy pressing plate is fixed on bearing surface.
3. according to claim a kind of sectional type aircraft skin fast joint structure, is characterized in that, the length and width of described left section or right section are 5000mm × 1000mm, and thickness is 0.5mm ~ 2.5mm.
4. according to claim a kind of sectional type aircraft skin fast joint structure, is characterized in that, the peel strength of mushroom-head industry sticking belt is less than or equal to 6.66N/cm
-1, and the mushroom head diameter in the first mushroom fastener and the second mushroom fastener is more than or equal to for 0.26mm.
5., according to the method for making of the arbitrary described sectional type aircraft skin fast joint structure of claim 1-4, it is characterized in that, comprise the following steps:
(1) according to version and the processing technology of aircraft, rational covering segmented version is selected;
(2) the mushroom-head industry sticking belt of suitable carrying scope is selected; According to the segmented version determination sticking belt size of aircraft skin, sticking belt length equals covering length, and width equals the bearing surface width half of truss;
(3) parts that step (1) is determined are processed, comprise the cleaning of the bearing surface of covering burr and aircraft truss, the bearing surface of covering burr and aircraft truss should keep cleaning, dry;
(4) laying of mushroom head industry sticking belt on covering, stickup is completed;
First the first mushroom fastener is pasted respectively the lower surface of adjacent left section and right section by the mode of heating, then the second mushroom fastener is pasted on the upper surface of the bearing surface of truss by the mode heated;
(5) the mushroom-shaped fastener in compacting sticking belt both sides; The second mushroom fastener that adjacent left section bonds with the first mushroom fastener and the bearing surface upper surface of right section of covering lower surface is withheld;
(6) the fixing of aluminum alloy pressing plate is completed; The aluminum alloy pressing plate being used for compressing covering is fitted in the upper surface place of left and right section of adjacent part, and aluminum alloy pressing plate is fixed on the bearing surface of truss;
(7), after said structure installation, the structural adjustment of integrated airplane covering is carried out.
6. the method for making of sectional type aircraft skin fast joint structure according to claim 5, is characterized in that, in step (4), type of heating adopts heating rod heating, and heating-up temperature is less than or equal to 55 DEG C.
7. the method for making of sectional type aircraft skin fast joint structure according to claim 5, it is characterized in that, described bearing surface and aluminum alloy pressing plate are all provided with at least two knock holees, hole on aluminum alloy pressing plate and the hole coaxial positioning on bearing surface, then with flathead screw, aluminum alloy pressing plate is fixed on truss on bearing surface.
8. the method for making of sectional type aircraft skin fast joint structure according to claim 5, it is characterized in that, in step (5), be by the roller of 10kg by fastening part when not by roll extrusion when additional force effect 5 times, finally realize first, second mushroom fastener compacting.
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105235890A (en) * | 2015-10-19 | 2016-01-13 | 北京航空航天大学 | Aircraft wing structure capable of realizing rapid disassembly and assembly for cell array |
| CN106043735A (en) * | 2016-05-31 | 2016-10-26 | 中国航空工业集团公司西安飞机设计研究所 | Rigidity-equivalent wing static gas spring model |
| CN106114915A (en) * | 2016-08-26 | 2016-11-16 | 西安融智航空科技有限公司 | A kind of safeguard structure of interconnected carrying heat-insulation integrative |
| CN107161318A (en) * | 2016-03-07 | 2017-09-15 | 上海奥科赛飞机有限公司 | The stressed-skin construction and its preparation technology of a kind of solar powered aircraft |
| CN110186640A (en) * | 2019-06-21 | 2019-08-30 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | A kind of wing wind tunnel model manufacturing method and wing wind tunnel model |
| CN110690548A (en) * | 2019-10-11 | 2020-01-14 | 中国电子科技集团公司第二十九研究所 | Parabolic cylinder antenna structure without die forming and manufacturing method |
| CN107161318B (en) * | 2016-03-07 | 2024-04-19 | 上海奥科赛飞机有限公司 | Skin structure of solar aircraft and preparation process thereof |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105235890A (en) * | 2015-10-19 | 2016-01-13 | 北京航空航天大学 | Aircraft wing structure capable of realizing rapid disassembly and assembly for cell array |
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| CN110186640A (en) * | 2019-06-21 | 2019-08-30 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | A kind of wing wind tunnel model manufacturing method and wing wind tunnel model |
| CN110186640B (en) * | 2019-06-21 | 2024-04-12 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Wing wind tunnel model manufacturing method and wing wind tunnel model |
| CN110690548A (en) * | 2019-10-11 | 2020-01-14 | 中国电子科技集团公司第二十九研究所 | Parabolic cylinder antenna structure without die forming and manufacturing method |
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| CN104787301B (en) | 2017-09-29 |
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Effective date of registration: 20190225 Address after: 213000 No. 199 Fenglin South Road, Wujin High-tech Industrial Development Zone, Changzhou City, Jiangsu Province Co-patentee after: Xinyu Defense Technology Co., Ltd. Patentee after: New United Group Co., Ltd. Address before: 213164 Fenglin Road 68, hi tech Industrial Development Zone, Wujin District, Changzhou, Jiangsu Patentee before: New United Group Co., Ltd. |
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